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The Williams F107 (company designation WR19) is a small turbofan engine made by Williams International.The F107 was designed to propel cruise missiles.It has been used as the powerplant for the AGM-86 ALCM, and BGM-109 Tomahawk, as well as the experimental Kaman KSA-100 SAVER and Williams X-Jet flying platform.
The F124 engine is a low-bypass, two-spool engine (meaning that there are two rotating shafts, a high-pressure shaft and a low-pressure shaft). The fan/low-pressure compressor has three stages with titanium blades. The first stage has 30 blades, [19] and the overall pressure ratio for the three-stage fan is 2.5:1. Some of the air is bypassed ...
Average fuel consumption is about 950 lb. per hour for a 7,765 lbf engine on a G280, to be compared to 875 lb. per hour for a 4,420 lbf TFE731 on a G150. [3] More than 3.5 million flight hours have been logged till October 2017, and the 2,000th engine should be delivered in 2018. [2] Honeywell maintenance program is $447 for two engines per ...
The engine has an overall pressure ratio of 35:1, which is extremely high for an engine with a centrifugal compressor. Other cycle parameters are a bypass ratio of 5.3 and airflow of 240 lb/s (108.9 kg/s).
In December 1980, Pratt & Whitney changed to a new naming system for its engines and the JT10D became the PW2037. The PW2000 is a dual-spool, axial air flow, annular combustion, high bypass turbofan with a dual-channel full authority digital engine control system. It was certified in 1984 as the first civilian FADEC-controlled aviation engine.
The Garrett TFE731 (now Honeywell TFE731) is a family of geared turbofan engines commonly used on business jet aircraft. Garrett AiResearch originally designed and built the engine, which due to mergers was later produced by AlliedSignal and now Honeywell Aerospace.
The engine has a wide-chord swept fan, two-stage low-pressure compressor and counter rotating high-pressure compressor based on a titanium impeller, for a 2,050 lbf (9.1 kN) takeoff thrust. [5] The HF120 engine's components interact with greater efficiency by incorporating 3D aerodynamic design, and its effusion-cooled combustor design emits ...
PW205B First run 1987. Flown in twin-engine MBB BO105 for demonstration only. [2]PW206A Maximum continuous power 550 shp (410 kW) [3] for use on the MD Explorer PW206B Maximum continuous power 431 shp (321 kW), [3] for use on the Eurocopter EC135